(19)
(11) EP 0 469 784 A3

(12) EUROPEAN PATENT APPLICATION

(88) Date of publication A3:
24.03.1993 Bulletin 1993/12

(43) Date of publication A2:
05.02.1992 Bulletin 1992/06

(21) Application number: 91306779.9

(22) Date of filing: 25.07.1991
(51) International Patent Classification (IPC)5: F01D 5/08
(84) Designated Contracting States:
DE FR GB IT

(30) Priority: 30.07.1990 US 560538

(71) Applicant: GENERAL ELECTRIC COMPANY
Schenectady, NY 12345 (US)

(72) Inventors:
  • Lee, Ching-Pang
    Cincinnati, Ohio 45249 (US)
  • Shelton, Monty Lee
    Cincinnati, Ohio 45208 (US)
  • Mason, Harvey Waldo
    Loveland, Ohio 45140 (US)
  • Carlson, Clay Kyle
    Cincinnati, Ohio 45208 (US)
  • Rieck, Harold Paul, Jr.
    West Chester, Ohio 45069 (US)
  • Hauser, Ambrose Andreas
    Wyoming, Ohio 45215 (US)

(74) Representative: Pratt, Richard Wilson et al
London Patent Operation G.E. Technical Services Co. Inc. Essex House 12/13 Essex Street
London WC2R 3AA
London WC2R 3AA (GB)


(56) References cited: : 
   
       


    (54) Aft entry cooling system and method for an aircraft engine


    (57) An aft entry system (12) in a gas turbine engine (10) is provided for cooling selected one or more of aft high and low pressure turbine stages of the engine. The aft entry system includes an air flow circuit (60) for routing low pressure cooling air radially outward from an interstage region of a multi-stage compressor of a core engine (20) of the gas turbine engine and axially in an aft direction to a plurality of radial passages, such as provided by stationary stator and outlet guide vanes (64), which provide an aft entry region to the selected high and low pressure turbine stages. The pressure of the cooling air routed by the air flow circuit (66) of the aft entry system (12) can be lower than the pressure of air at a discharge end of the compressor (24) but higher than the pressure of the gas stream discharging from the selected turbine stage.






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